CN109765030B - Wind tunnel thermal jet interference test device - Google Patents
Wind tunnel thermal jet interference test device Download PDFInfo
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- CN109765030B CN109765030B CN201910183393.7A CN201910183393A CN109765030B CN 109765030 B CN109765030 B CN 109765030B CN 201910183393 A CN201910183393 A CN 201910183393A CN 109765030 B CN109765030 B CN 109765030B
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- 238000012360 testing method Methods 0.000 title claims abstract description 41
- 239000002184 metal Substances 0.000 claims abstract description 20
- 238000005338 heat storage Methods 0.000 claims abstract description 10
- 238000005485 electric heating Methods 0.000 claims description 25
- 229910001220 stainless steel Inorganic materials 0.000 claims description 11
- 239000010935 stainless steel Substances 0.000 claims description 11
- 238000009413 insulation Methods 0.000 claims description 7
- CPLXHLVBOLITMK-UHFFFAOYSA-N Magnesium oxide Chemical compound [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 claims description 6
- 239000007921 spray Substances 0.000 claims description 6
- 229910001208 Crucible steel Inorganic materials 0.000 claims description 3
- 239000012774 insulation material Substances 0.000 claims description 3
- 239000000395 magnesium oxide Substances 0.000 claims description 3
- 239000000843 powder Substances 0.000 claims description 3
- 238000004321 preservation Methods 0.000 claims description 3
- 238000009423 ventilation Methods 0.000 abstract description 7
- 230000005540 biological transmission Effects 0.000 abstract description 2
- 239000003638 chemical reducing agent Substances 0.000 abstract 2
- 238000010438 heat treatment Methods 0.000 abstract 1
- 230000001105 regulatory effect Effects 0.000 abstract 1
- 238000000465 moulding Methods 0.000 description 12
- 238000010586 diagram Methods 0.000 description 5
- 238000011160 research Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a wind tunnel thermal jet interference test device. The device comprises an air supply system, an air storage tank and a heater which are sequentially connected through metal pipelines, and the air storage tank and the heater are sequentially connected to the jet engine through flexible hoses. The air supply system comprises an air source tank area, an air transmission pipeline and an adjusting control valve. Test gas with a set proportion is stored in the gas storage tank. The heater is a heat storage type heater, the heater adopts a structure form that a heating pipe, a ventilation pipeline and a heat storage block are integrally cast, thermocouples are respectively arranged in the heater, at the outlet and at the air utilization point, and the temperature of the air utilization point is accurately controlled through a temperature control device. During test, gas in the gas storage tank enters the heater through the linkage control of the pressure reducer, then flows into the jet engine resident chamber through the flexible hose and the ventilation supporting rod, and the pressure of the resident chamber gas is regulated to a target value through the pressure reducer. The wind tunnel thermal jet interference test device is suitable for wind tunnel thermal jet tests in a lean atmosphere environment, and has the advantages of simplicity and convenience in operation and reliability in operation.
Description
Technical Field
The invention belongs to the field of wind tunnel test devices, and particularly relates to a wind tunnel thermal jet interference test device.
Background
Compared with the traditional control surface control, the jet flow control technology has the characteristics of full speed domain and full airspace control, and has the advantages of high response speed and high control precision. However, the interference of the jet flow and the incoming flow is a complex flow phenomenon, and the current research is not deep enough.
At present, researchers mostly conduct cold jet flow interference test researches, and the hot jet flow interference test researches are very few because the existing solid charge rocket engine simulates a real jet flow engine to have the problems of unstable jet flow resident chamber pressure, low efficiency, short effective test time and the like. And the research field of the thermal jet simulation test in the lean atmosphere environment is almost blank.
Along with the great application of jet control technology in aircrafts and the continuous improvement of the jet control precision requirement, the thermal jet interference wind tunnel test requirement is also continuously enhanced.
Currently, research and development of related test devices for thermal jet interference effect in a lean atmosphere are needed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a wind tunnel thermal jet interference test device.
The invention relates to a wind tunnel thermal jet interference test device which is characterized by comprising a gas supply system, a gas storage tank and a heater which are sequentially connected through metal pipelines, and a jet engine which is sequentially connected through flexible hoses;
The air supply system comprises two air paths, one air path is a CF 4 air path, the front end of the CF 4 air path comprises a plurality of CF 4 air tanks which are connected in parallel, each CF 4 air tank is connected with a valve, and the rear end of the CF 4 air path is connected with a pressure reducing valve and a film press I and then is led into an air storage tank; the other path of air passage is an N 2 air passage, the front end of the N 2 air passage comprises a plurality of N 2 air tanks which are connected in parallel, a valve is connected to each N 2 air tank, and the rear end of the N 2 air passage is connected with a pressure reducing valve and a film press II and then is led into an air storage tank; pressure sensors are arranged in front of and behind the pressure reducing valve to measure the pipeline pressure. The test gas is selected by controlling the opening and closing of the valve, and when the mixed gas is needed, each gas sequentially flows into the film press for pressurization and then enters the gas storage tank. The proportion of the gas is controlled by controlling the pressure of the gas filled into the gas storage tank;
The heater comprises an electric heating tube, a junction box, a heater shell and an electric heating tube mounting plate, wherein a plurality of groups of electric heating tubes are mounted on the electric heating tube mounting plate, the electric heating tubes are inserted into the heater shell, the junction box is further mounted on the electric heating tube mounting plate, and the junction box supplies power to the electric heating tubes through an external power supply; the lower part of the heater shell is provided with an air inlet, and the upper part of the heater shell is provided with an air outlet;
The metal pipeline is a hollow pipeline, the center of the hollow pipeline is a gas circuit pipeline, the inner layer of the hollow pipeline is an electric heating wire, the middle layer of the hollow pipeline is a heat insulation inner bushing to reduce gas heat diffusion and the rise of the temperature of the metal pipeline, and the outer layer of the hollow pipeline is a metal jacket; connecting flanges I are arranged at two ends of the metal pipeline;
The flexible hose is a soft hollow pipe, the center of the hollow pipe is a stainless steel corrugated hose, the inner layer of the hollow pipe is a heat-insulating sleeve, the middle layer of the hollow pipe is an electric heating wire, the outer layer of the hollow pipe is a stainless steel woven net, and connecting flanges II are arranged at two ends of the flexible hose;
After the connecting flange I is connected with the connecting flange II, the air flow of the air channel pipeline is led into a stainless steel corrugated hose of the flexible hose, then flows into a wind tunnel test section, and then flows into the jet engine through a balance strut;
The jet engine comprises a jet engine shell, a spray pipe and a residence chamber, wherein a cavity in the jet engine shell is the residence chamber, an air inlet of the jet engine is formed in the inlet of the residence chamber, and the spray pipe is arranged at the outlet of the residence chamber. The nozzle is designed according to the area ratio to ensure the Mach number of the jet outlet. The jet engine is isolated from the balance and cannot interfere with the balance, so that the jet engine is prevented from influencing the balance force measurement in the test process;
The air pressure range in the metal pipeline in front of the molding press I and the molding press II is 0.5-14 MPa, and the outlet pressure of the molding press I and the molding press II is 14.2MPa;
thermocouples are installed in the heater and the air outlet, and the temperature of the air point is accurately controlled by the temperature control device.
The inside of the electric heating tube is filled with magnesia powder for ensuring insulation with the electric heating wire;
the heat storage block is filled in the heater, the heat storage block is made of cast steel, and the heat storage block is wrapped by a commercially available heat insulation material to reduce heat loss of the heat storage block;
The wind tunnel thermal jet interference test device provided by the invention has the advantages that the effective test operation time is more than or equal to 30s, the total jet pressure is less than or equal to 10MPa, the jet flow is less than or equal to 0.25kg/s, the device is suitable for thermal jet interference test in a thin atmospheric environment, and the device is simple and convenient to operate and reliable in operation.
Drawings
FIG. 1 is a schematic diagram of a wind tunnel thermal jet interference test device of the present invention;
FIG. 2 is a schematic diagram of an air supply system in the wind tunnel thermal jet interference test device of the invention;
FIG. 3 is a schematic diagram of a heater in the wind tunnel thermal jet disturbance test device of the present invention;
FIG. 4 is a schematic diagram of a metal pipeline in the wind tunnel thermal jet interference test device of the invention;
FIG. 5 is a schematic view of a flexible hose in the wind tunnel thermal jet disturbance test device of the present invention;
FIG. 6 is a schematic view of a jet engine in a wind tunnel thermal jet disturbance test device according to the present invention;
FIG. 7 is a schematic installation diagram of a wind tunnel thermal jet interference test device according to the invention;
In the figure, 1, a gas supply system 2, a gas storage tank 3, a heater 4, a metal pipe 5, a flexible hose 6, a jet engine 7, a model 8, a nozzle 9, a balance 10, a ventilation support rod 11 and a balance support rod;
CF 4 gas tank 102N 2 gas tank 103, valve 104, pressure sensor 105, pressure reducing valve 106, molding press I107, molding press II;
301. electrothermal tube 302, air inlet 303, air outlet 304, junction box 305, heater shell 306, electrothermal tube mounting plate;
401. Gas circuit pipeline 402, metal jacket 403, heat insulation inner bushing 404, electric heating wire 405 and connecting flange I;
501. Stainless steel corrugated hose 502, stainless steel woven net 503, heat preservation sleeve 504 and connecting flange II;
601. Jet housing 602, nozzle 603, dwell chamber 604, jet intake.
Detailed description of the preferred embodiments
The invention is described in detail below with reference to the drawings and examples.
As shown in fig. 1, the wind tunnel thermal jet interference test device of the invention comprises a gas supply system 1, a gas storage tank 2 and a heater 3 which are sequentially connected through a metal pipeline 4, and a jet engine 6 which is sequentially connected through a flexible hose 5;
As shown in fig. 2, the air supply system 1 includes two air paths, one air path is a CF 4 air path, the front end of the CF 4 air path includes a plurality of parallel CF 4 air tanks 101, each CF 4 air tank 101 is connected with a valve 103, the rear end of the CF 4 air path is connected with a pressure reducing valve 105 and a film press i 106, and then the air is introduced into the air storage tank 2; the other path of air passage is an N 2 air passage, the front end of the N 2 air passage comprises a plurality of N 2 air tanks 102 which are connected in parallel, a valve 103 is connected to each N 2 air tank 102, the rear end of the N 2 air passage is connected with a pressure reducing valve 105 and a film press II 107, and then the air is introduced into an air storage tank 2; the pressure sensor 104 is arranged at the front and the back of the pressure reducing valve 105 to measure the pipeline pressure;
As shown in fig. 3, the heater 3 includes an electrothermal tube 301, a junction box 304, a heater housing 305 and an electrothermal tube mounting plate 306, wherein a plurality of groups of electrothermal tubes 301 are mounted on the electrothermal tube mounting plate 306, a plurality of groups of electrothermal tubes 301 are inserted into the heater housing 305, a junction box 304 is also mounted on the electrothermal tube mounting plate 306, and the junction box 304 supplies power to the electrothermal tubes 301 through an external power supply; the lower part of the heater shell 305 is provided with an air inlet 302, and the upper part of the heater shell 305 is provided with an air outlet 303;
As shown in fig. 4, the metal pipe 4 is a hollow pipe, the center of the hollow pipe is a gas path pipe 401, the inner layer of the hollow pipe is an electric heating wire 404, the middle layer of the hollow pipe is a heat insulation inner bushing 403, and the outer layer of the hollow pipe is a metal jacket 402; connecting flanges I405 are arranged at two ends of the metal pipeline 4;
as shown in fig. 5, the flexible hose 5 is a flexible hollow pipe, the center of the hollow pipe is a stainless steel corrugated hose 501, the inner layer of the hollow pipe is a heat insulation sleeve 503, the middle layer of the hollow pipe is an electric heating wire 404, the outer layer of the hollow pipe is a stainless steel woven net 502, and connecting flanges ii 504 are installed at two ends of the flexible hose 5;
After the connecting flange I405 is connected with the connecting flange II 504, the air flow of the air channel pipeline 401 is led into the stainless steel corrugated hose 501 of the flexible hose 5;
As shown in fig. 6, the jet engine 6 comprises a jet engine housing 601, a spray pipe 602 and a standing chamber 603, wherein a cavity in the jet engine housing 601 is the standing chamber 603, an inlet 604 of the jet engine is arranged at the inlet of the standing chamber 603, and the spray pipe 602 is arranged at the outlet of the standing chamber 603;
the air pressure range in the metal pipeline 4 in front of the molding press I106 and the molding press II 107 is 0.5-14 MPa, and the outlet pressure of the molding press I106 and the molding press II 107 is 14.2MPa;
thermocouples are arranged in the heater 3 and at the air outlet 303;
the inside of the electric heating tube 301 is filled with magnesia powder;
the heat storage block is filled in the heater 3, the heat storage block is made of cast steel, and the heater 3 is wrapped with a commercially available heat preservation and insulation material.
Example 1
The specific working procedure of this embodiment is as follows:
1. Preparation before test
And installing each gas transmission pipeline, ensuring the normal supply of water, electricity and gas and checking each device.
2. Installation test model
As shown in fig. 7, the balance bar 11 is first mounted on the wind tunnel knife bending mechanism, then the balance 9, the model 7 and the jet engine are mounted on the balance bar 11, the ventilation bar 10 is positioned inside the balance bar 11, the ventilation bar 10 is coaxial with the balance bar 11, and the front end of the ventilation bar 10 is connected with the jet engine air inlet 604.
During the test, the air in the air storage tank enters the jet engine 6 through the ventilation supporting rod 10 and then is sprayed out of the model through the nozzle 8, the gap between the model 7 and the nozzle 8 is required to be adjusted in the installation process, and interference cannot be generated between the model 7 and the nozzle 8, so that the influence of jet acting force on balance force measurement is avoided.
3. Developing a model test
The valves 103 of the CF 4 gas tank 101 and the N 2 gas tank 102 are controlled to be opened and closed to select test gas, wherein the test gas comprises CF 4 and N 2, and when mixed gas is needed, each gas flows into the molding press I106 and the molding press II 107 in sequence, and then enters the gas storage tank 2 after being pressurized. The mixture ratio of the mixed gas is controlled by controlling the pressure of the CF 4 and N 2 gas filled into the gas storage tank 2.
The gas in the gas storage tank 2 enters the preheated heater 3.
The test air flows into the residence chamber of the jet engine 6 through the balance strut 11 after being heated by the heater 3, and is sprayed out, and after the flow field of the wind tunnel is stable, the aerodynamic force of the model 7 is measured.
Claims (3)
1. A wind tunnel thermal jet interference test device is characterized in that,
The device comprises an air supply system (1), an air storage tank (2) and a heater (3) which are sequentially connected through a metal pipeline (4), and a jet engine (6) which is sequentially connected through a flexible hose (5);
The air supply system (1) comprises two air paths, one air path is a CF 4 air path, the front end of the CF 4 air path comprises a plurality of CF 4 air tanks (101) which are connected in parallel, each CF 4 air tank (101) is connected with a valve (103), and the rear end of the CF 4 air path is connected with a pressure reducing valve (105) and a film press I (106) and then is led into the air storage tank (2); the other path of air passage is an N 2 air passage, the front end of the N 2 air passage comprises a plurality of N 2 air tanks (102) which are connected in parallel, a valve (103) is connected to each N 2 air tank (102), and the rear end of the N 2 air passage is connected with a pressure reducing valve (105) and a film press II (107) and then is led into an air storage tank (2); pressure sensors (104) are arranged at the front and the back of the pressure reducing valve (105) to measure the pipeline pressure;
The heater (3) comprises an electric heating tube (301), a junction box (304), a heater shell (305) and an electric heating tube mounting plate (306), wherein a plurality of groups of electric heating tubes (301) are mounted on the electric heating tube mounting plate (306), the electric heating tubes (301) are inserted into the heater shell (305), the junction box (304) is further mounted on the electric heating tube mounting plate (306), and the junction box (304) supplies power for the electric heating tubes (301) through an external power supply; an air inlet (302) is formed in the lower portion of the heater shell (305), and an air outlet (303) is formed in the upper portion of the heater shell (305);
the metal pipeline (4) is a hollow pipeline, the center of the hollow pipeline is a gas circuit pipeline (401), the inner layer of the hollow pipeline is an electric heating wire (404), the middle layer of the hollow pipeline is a heat insulation inner bushing (403), and the outer layer of the hollow pipeline is a metal jacket (402); connecting flanges I (405) are arranged at two ends of the metal pipeline (4);
The flexible hose (5) is a flexible hollow pipe, the center of the flexible hollow pipe is a stainless steel corrugated hose (501), the inner layer of the flexible hollow pipe is a heat insulation sleeve (503), the middle layer of the flexible hollow pipe is an electric heating wire (404), the outer layer of the flexible hollow pipe is a stainless steel woven net (502), and connecting flanges II (504) are arranged at two ends of the flexible hose (5);
After the connecting flange I (405) is connected with the connecting flange II (504), the air flow of the air channel pipeline (401) is led into the stainless steel corrugated hose (501) of the flexible hose (5);
The jet engine (6) comprises a jet engine shell (601), a spray pipe (602) and a residence chamber (603), wherein a cavity in the jet engine shell (601) is the residence chamber (603), an inlet of the residence chamber (603) is provided with a jet engine air inlet (604), and an outlet of the residence chamber (603) is provided with the spray pipe (602);
The air pressure range in the metal pipeline (4) in front of the film press I (106) and the film press II (107) is 0.5-14 MPa, and the outlet pressure of the film press I (106) and the film press II (107) is 14.2MPa;
Thermocouples are arranged in the heater (3) and the air outlet (303).
2. The wind tunnel thermal jet disturbance testing device according to claim 1, wherein the device comprises a plurality of nozzles,
The inside of the electric heating tube (301) is filled with magnesia powder.
3. The wind tunnel thermal jet disturbance testing device according to claim 1, wherein the device comprises a plurality of nozzles,
The heat storage block is filled in the heater (3), the heat storage block is made of cast steel, and the heat preservation and heat insulation material is wrapped outside the heater (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910183393.7A CN109765030B (en) | 2019-03-12 | 2019-03-12 | Wind tunnel thermal jet interference test device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910183393.7A CN109765030B (en) | 2019-03-12 | 2019-03-12 | Wind tunnel thermal jet interference test device |
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| CN109765030A CN109765030A (en) | 2019-05-17 |
| CN109765030B true CN109765030B (en) | 2024-04-19 |
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Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595722A (en) * | 2019-11-01 | 2019-12-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Heat-preservation flexible hose for hypersonic wind tunnel heat jet flow interference test |
| CN110595723A (en) * | 2019-11-01 | 2019-12-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel heat jet flow interference test gas heater |
| CN111982458A (en) * | 2020-08-20 | 2020-11-24 | 北京航空航天大学 | Interference simulation system |
| CN112985751B (en) * | 2021-02-01 | 2022-09-23 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel stable section total temperature and total pressure test bent frame structure and manufacturing method |
| CN113740023B (en) * | 2021-08-31 | 2024-02-09 | 中国航天空气动力技术研究院 | Novel jet flow supporting rod |
| CN113588201B (en) * | 2021-09-30 | 2022-04-12 | 中国空气动力研究与发展中心超高速空气动力研究所 | Thermal jet flow interference test device and test method for high-altitude high-speed thin environment |
| CN114813025B (en) * | 2021-12-28 | 2024-06-25 | 中国航天空气动力技术研究院 | Gas generating device for thermal spraying interference wind tunnel test |
| CN114509234B (en) * | 2022-04-20 | 2022-07-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | Flexible pipeline device for mixed heating gas jet flow gas supply of hypersonic wind tunnel |
| CN115112343B (en) * | 2022-06-24 | 2023-09-29 | 中国船舶科学研究中心 | Smoke flow generating device applied to wind tunnel smoke flow test and application method |
| CN115556964B (en) * | 2022-11-21 | 2023-03-10 | 中国飞机强度研究所 | Spray test air supply device and method for aircraft test |
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